RU2154003C2 - Connection of wing and fuselage - Google Patents

Abstract

FIELD: aeronautical engineering. SUBSTANCE: wing is secure to main frames 3 of fuselage. Each torsion box 1 of half-wing intersecting side panels of fuselage skin extends inside fuselage over distance limited by width of fuselage functional compartment 2. All fuselage frames 3 located on section of wing torsion box 1 are main frames. Structural depths of side members of main frames 3 are limited by width of fuselage functional compartment 2. Upper and lower panels of skin of torsion box 1 of each half-wing are connected inside fuselage with walls of side members of main frames 3 by means of continuous or multiple-spot seams. EFFECT: extended field of selection for rational positioning of torsion-box-type wings in fuselage height; possibility of using fuselage volume in mid-wing monoplane configuration due to exclusion of central part of torsion-box from wing construction for increase of functional compartment. 4 dwg

Description

 The invention relates to the field of aeronautical engineering, in particular, to the construction of the connection of the mid-height coffer or monoblock wing with the fuselage.

 The connection of the wing and the fuselage is one of the most loaded areas of the airframe design, in which large-scale forces are transferred from the wing to the power elements of the fuselage. A design is known in which the wing box is not interrupted inside the fuselage (Michael C. Y. Niu. Airframe Structural Design. Hong Kong: Conmilit Press LTD, 1988, p. 406., fig. 11.5.1 (d)). The wing with the fuselage is connected by attaching each wing spar to the corresponding power frame of the fuselage.

The disadvantages of the known design are:
- a sharp deterioration in the layout characteristics of the fuselage, virtually eliminating the use of a mid-plane scheme for passenger and transport aircraft (Aviation. Encyclopedia. M: Big Russian Encyclopedia. 1994, p. 357.);
- high intensity of effort in the connection zone;
- reducing the resource of the structure in the connection zone;
- the presence of lightly loaded walls of the side members in the area between the sides of the fuselage;
- increased weight of the structure.

 A known wing-fuselage connection design, selected as a prototype, in which the wing box is bounded by the fuselage side, the fuselage power frames are connected to the wing spars, and the fuselage skin panels are connected to the wing box panels (Michael CY Niu. Airframe Structural Design. Hong Kong: Conmilit Press LTD, 1988, fig. 11.5.1 (c); Results of science and technology, Aircraft manufacturing, Vol. 2, part II. M: VINITI, 1976, Fig. 132).

The disadvantages of the known design are:
- the presence of a transverse junction of the wing with the fuselage in a heavily loaded area near the side of the fuselage, which leads to a decrease in resource and an increase in the mass of the structure;
- the transfer of loads from the wing to the fuselage is effective only for aircraft integrated circuit. When the fuselage cross section is large enough in comparison with the wing height, the side panels of the fuselage and the wing panels are at an angle close to the straight line. Their interaction in the transfer of normal forces acting in the wing panels is not effective.

 The task is to develop such a combination of the caisson or monoblock wing and the fuselage in the mid-plane scheme, which will increase the efficiency of the aircraft due to the better use of the internal volume of the fuselage, reduce weight and increase the life of the structure.

 The problem is solved due to the fact that in the connection of the wing and the fuselage, carried out by attaching the wing box to the power frames of the fuselage, according to the invention, the box of each half wing, crossing the side panels of the fuselage skin, is extended inside the fuselage by a distance limited by the width of the functional compartment of the fuselage. All fuselage frames located on the wing caisson section are made of power, and the upper and lower panels of the casing of each half wing are connected inside the fuselage with the walls of the power frames by continuous or multipoint seams. The structural heights of the frames are also limited by the width of the functional compartment of the fuselage, which is determined by the requirements of the layout of the aircraft.

 The connection provides the transfer of large normal forces from the panels of the wing box to the fuselage in a distributed form and, as a result, a longer life and lower weight of the structure. The functional compartment of the fuselage remains free of wing structure elements.

 Thus, the claimed method of connecting the wing and the fuselage meets the criteria of the invention of "novelty."

 Comparison of the claimed solution not only with the prototype, but also with other technical solutions protected by patents in this technical field did not allow to reveal in them the features that distinguish the claimed solution from the prototype, which allows us to conclude that the criterion is "inventive step".

The invention is illustrated by drawings, where
in FIG. 1 is a cross-sectional view of the central part of an airplane glider,
in FIG. 2 shows a section AA
in FIG. 3 shows a section bB,
in FIG. 4 shows the assembly A in FIG. 1.

 The caisson 1 of each half-wing is extended inside the fuselage by a distance limited by the functional compartment 2. All frames 3 located on the section of the caisson 1 are made of power, their building heights are also limited by the width of the functional compartment 2 of the fuselage. The caisson 1 of each half-wing has a side 4 and root 5 ribs. Parts of the frames 3 located above the caissons and under the caissons 1 of each half wing are interconnected through the walls of the side members 6 or through special walls 7 installed in the caissons 1 between the side 4 and root 5 ribs. The connection of the upper and lower panels of the casing of the caissons 1 with the walls of the frames 3 is made by means of parts 8, and with the casing 9 of the fuselage by means of profiles 10. The walls 6 and 7 are connected to the side ribs 4 of the racks 11. All connections are made by continuous or multipoint seams. In figures 1 ... 3, the seams are shown in bold lines.

 Details 8 transmit in normal form to the walls of the power frames 3 normal forces acting in the panels of the skin of the caissons 1 from the bend of the wing.

 Racks 11 transmit cutting forces from the walls of the side members 6 to the power frames 3.

 The profiles 10 transmit forces to the fuselage skin 9 in the casing panels 1, acting along the axis of the fuselage.

The inventive connection of the wing with the fuselage provides a new technical effect, which consists in:
- the best use of the internal volume of the fuselage in the midplane scheme by eliminating the central part of the center section box from the wing structure and using the vacated volume to increase the functional compartment of the fuselage;
- expanding opportunities for choosing the rational placement of the wing along the height of the fuselage;
- reducing the mass and increasing the life of the structure by reducing the forces transmitted by the power frames of the fuselage connected to the side members of the wing, by including all frames located on the section of the wing box and, as a result, reducing the concentration of forces in the power frames; reducing the concentration of effort in the root part of the wing in areas near the spars; the absence of lightly loaded in the known wall structures spars of the central part of the center section box excluded from the wing structure in the proposed solution.

 The greatest effect of the use of the proposed solution can be achieved for aircraft in which the width of the cross section of the fuselage is greater than its height, for example, for aircraft with aerodynamically bearing fuselages.

Claims (1)

 The connection of the wing and the fuselage by fixing the wing to the power frames of the fuselage, characterized in that the caisson of each half wing, crossing the side panels of the fuselage skin, is extended inside the fuselage by a distance limited by the width of the functional compartment of the fuselage, all the fuselage frames located on the wing section power, the construction heights of their sidewalls are also limited by the width of the functional compartment of the fuselage, and the upper and lower panels of the casing of each half wing are connected inside the fuselage with the walls of the sides of the power frames continuous or multipoint seams.

Images